CN102472115A - Turbine housing - Google Patents
Turbine housing Download PDFInfo
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- CN102472115A CN102472115A CN2010800293214A CN201080029321A CN102472115A CN 102472115 A CN102472115 A CN 102472115A CN 2010800293214 A CN2010800293214 A CN 2010800293214A CN 201080029321 A CN201080029321 A CN 201080029321A CN 102472115 A CN102472115 A CN 102472115A
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- pillar
- turbine
- moving blade
- sheet metal
- turbine moving
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- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 41
- 239000002184 metal Substances 0.000 claims abstract description 24
- 230000001154 acute effect Effects 0.000 claims abstract description 9
- 230000005284 excitation Effects 0.000 claims description 16
- 238000005520 cutting process Methods 0.000 description 15
- 238000003466 welding Methods 0.000 description 7
- 238000003754 machining Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 3
- RKTYLMNFRDHKIL-UHFFFAOYSA-N copper;5,10,15,20-tetraphenylporphyrin-22,24-diide Chemical compound [Cu+2].C1=CC(C(=C2C=CC([N-]2)=C(C=2C=CC=CC=2)C=2C=CC(N=2)=C(C=2C=CC=CC=2)C2=CC=C3[N-]2)C=2C=CC=CC=2)=NC1=C3C1=CC=CC=C1 RKTYLMNFRDHKIL-UHFFFAOYSA-N 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000003054 catalyst Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000008030 elimination Effects 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- 239000012467 final product Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000003032 molecular docking Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910001566 austenite Inorganic materials 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004021 metal welding Methods 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000000746 purification Methods 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/026—Scrolls for radial machines or engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/12—Control of the pumps
- F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
Abstract
Provided is a sheet-metal turbine housing 1 in which a scroll part is formed by joining opposing scroll members made of sheet metal to form a spiral-shaped exhaust gas passage therein. The sheet-metal turbine housing 1 includes a member on a side of a bearing housing in which a bearing supporting a rotation shaft of a turbine rotor blade 50 is arranged; a member on a flow exhaust side which forms an outer side of the turbine rotor blade 50 in a direction of the turbine; and support columns 21, 40 which connect the member on the side of the bearing housing with the member on the flow exhaust side in an axial direction of the turbine and which are arranged at intervals on an outer circumferential side of the turbine rotor in a circumferential direction of the turbine rotor blade 50. Each of the support columns 21, 40 may have a cross-sectional shape in the axial direction of the turbine which includes an upstream corner and a downstream corner in a direction of a gas flow each of which has an acute angle, 1, 2 so that an upstream surface 32 and a downstream surface 34 incline along the gas flow.
Description
Technical field
The present invention relates to a kind of turbine shroud that is used for the sheet metal system of turbosupercharger; This turbosupercharger is utilized the energy of the exhaust gas of motor; Generation is for the supercharging of motor; Particularly relate to a kind of corbeling, the parts of parts and outlet flange side of pedestal side that this corbeling will constitute the core of turbine shroud link.
Background technique
If turbine shroud thermal capacity is big, and be arranged on the upstream side of exhaust emission control catalyst, then can become the obstacle of catalyzer heating installation.In recent years, see that utilize sheet metal to make housing thin-wall light-weighted, and reduce thermal capacitance, this makes catalyst activityization, and raising catalyzer purification function aspect is important from the viewpoint that the restriction of exhaust gas is strengthened.
When the turbine shroud of the sheet metal system of employing; Because sheet metal is thin and intensity is low; Therefore, be necessary to be provided with the parts on the cartridge housing side that disposes bearing and the fixing pillar part of parts binding of exhaust gas flowing path outlet side, the running shaft of this bearing supporting turbine moving blade.Yet owing to the mode of crossing the stream that flows into turbine moving blade with the outer circumferential side at turbine moving blade is provided with pillar, therefore, air-flow will receive the obstruction of pillar, thereby causes the performance of turbine efficiency reduction and pressurized machine to reduce.
About this pillar; In the prior art; In special permission document 1 ((Japan) special table 2006-527322 communique), disclose pad (pillar) 01, shown in figure 11, the structure of exhaust driven gas turbine 02 is: the housing 04 that the set inside of the outer shell 03 outside covering has volute; In this housing 04, between the forming box 07 of bearer ring 05 that adjustable guide plate is used and flowing path outlet side, be provided with the pad 01 that they are linked.To cross this pad is set towards the mode of the inflow stream 09 radially of turbine moving blade.
On the other hand, be well known that, about relevant existing technology, in special permission document 2 (spy opens the 2008-57448 communique), special permission document 3 (special table 2003-536009 communique) etc. also motion the turbine shroud structure of sheet metal system.
The existing technology document
The special permission document
Special permission document 1: (Japan) special table 2006-527322 communique
Special permission document 2: (Japan) spy opens the 2008-57448 communique
Special permission document 3: (Japan) special table 2003-536009 communique
Summary of the invention
The problem that invention will solve
Was yet not open in special permission document 1: pad 01 upwards with what kind of configuration relation configured in week? Perhaps, what kind of section shape does pad 01 form with respect to the exhaust gas that in stream, flows?
And; In special permission document 2,3, disclose, the volute portion of the turbine shroud of sheet metal system constitutes through two circumferential welding of metal plate components and edge about docking, yet; They openly do not form the structure of core of the central side of volute portion; Particularly do not disclose the structure of following pillar part, that is, the parts of parts and the exhaust gas flowing path outlet side on the turbine case side of the bearing of the running shaft that disposes the supporting turbine moving blade are linked fix.
Pillar is provided with the mode that the outer circumferential side at turbine moving blade crosses the stream that flows into turbine moving blade, and therefore, from reducing the aspect of flow path resistance, preferred pillar is superfine.Yet the aspect from the parts of the parts that link the rigid bearing case side and exhaust gas flowing path outlet side requires certain intensity.
And, owing to be configured in circumferential a plurality of pillars, circumferentially can produce variation in pressure at inflow gas; Thus; Can produce the excitation force of pressure wave,, then bring to hinder the turbine moving blade reliability problems if the natural vibration of this excitation force and turbine moving blade produces resonance.Therefore, in order to prevent the increase of specific excitation force, need to set configuration space, configuration number, the strut section shape of pillar.
Therefore; The present invention makes in view of the above problems; Its purpose is to provide a kind of pillar, its cross turbine mover blade outer circumferential side gas flow path and link the parts on the cartridge housing side that disposes bearing and the parts of exhaust gas flowing path outlet side, and these parts are integrated; The running shaft of said bearing supporting turbine moving blade; This pillar not only can reduce flow path resistance and improve outflow characteristic, and can avoid the resonance of turbine moving blade, improves the durability and the reliability of turbine moving blade.
The means of dealing with problems
In order to address the above problem; The present invention is a kind of sheet metal system turbine shroud; This turbine shroud is with the scroll member relative bonding of sheet metal system and form volute portion; This volute portion constitutes the exhaust gas stream of volute, wherein, circumferentially has the compartment of terrain on the outer circumferential side edge of turbine moving blade and disposes a plurality of pillars; This pillar links the running shaft of this bearing supporting turbine moving blade along turbine shaft to the parts to the parts on the cartridge housing side that is provided with bearing and the flowing path outlet side in the outside that forms turbine moving blade.
And in first invention, each pillar is that structure is at turbine shaft to the section shape of being seen: the upstream side bight and the bight, downstream side of air-flow form acute angle respectively, and upstream side and downstream side tilt along air-flow.
According to above-mentioned first invention; Utilize pillar along turbine shaft to the parts on the cartridge housing side that the is provided with bearing parts with the flowing path outlet side in the outside that forms turbine moving blade are linked; The running shaft of this bearing supporting turbine moving blade, this pillar turbine shaft to section shape be: the upstream side bight and the bight, downstream side of air-flow form acute angle respectively, and upstream side and downstream side tilt along air-flow; Therefore; With respect to making volute portion, can reduce area of contour and the area of contour of downstream side of the upstream side of pillar, thus while the air-flow that rotates towards central side; Can reduce by pillar cause to the gas stream flow channel resistance, can reduce the wake flow (flow and distort) that produces at the pillar rear.Its result can improve the mobile distortion of pillar wake flow, can improve the efficient and the reliability of turbine moving blade.
In addition; The section area of pillar need be the section area that can guarantee following rigidity and hardness; Promptly; Can link the parts on turbine case side and the parts of the flowing path outlet side in the outside that forms turbine moving blade, and can guarantee to make gap to keep certain rigid and hardness with turbine moving blade.
And the upstream side bight of the section shape of said pillar and the angle separately in bight, downstream side are 20 °～70 ° and get final product, through being set at such acute angle angle, can taking into account the pressure loss of guaranteeing pillar section area and minimizing air-flow.
And the section shape of said pillar is the roughly quadrilateral with inscribed circle arc, external circular arc, upstream side and downstream side, and any one of perhaps said inscribed circle arc or external circular arc do not have the general triangular of width.
The upstream side and the downstream side of above-mentioned pillar are made up of the plane respectively; Be roughly quadrilateral or general triangular on the whole, therefore, for circular binding parts; Process as follows easily: keep part as pillar through machining; And, through cutting cutting part therebetween, can be simply and carry out the processing and the manufacturing of pillar cheaply.
And; Second invention of the present invention is at foregoing (a kind of sheet metal system turbine shroud; The volute portion of the exhaust gas stream of formation volute forms through the volute portion of relative bonding sheet metal system; Wherein, dispose a plurality of pillars along circumferentially having the compartment of terrain at the outer circumferential side of turbine moving blade, this pillar along turbine shaft to the parts on the cartridge housing side that the is provided with bearing parts with the flowing path outlet side in the outside that forms turbine moving blade are linked; The running shaft of this bearing supporting turbine moving blade) on the basis; It is characterized in that, set the number of pillar through following mode, promptly; A pattern of the excitation force that the circumferential variation in pressure of the inflow gas that causes owing to these a plurality of pillars produces and the natural vibration of said turbine moving blade is in the slow-speed of revolution side resonance of operation range, and resonates with the rotating speed operation range outside more than the quadratic modes of the natural vibration of said turbine moving blade.
According to above-mentioned second invention; Owing to set the pillar number; A pattern of the excitation force that produces so that be configured in the circumferential variation in pressure of the inflow gas that circumferential a plurality of pillars cause and the natural vibration of said turbine moving blade is in the slow-speed of revolution side resonance of operation range; Therefore, prevent that a mode resonance stress of turbine moving blade is superfluous, the stress in the time of can reducing to resonate.
Usually, because the resonance of low order pattern produces big dynamic stress, therefore,, point of resonance is moved to slow-speed of revolution side, and can reduce to act on the dynamic stress of turbine moving blade as much as possible in order to avoid this low subresonance reliably.
And, set the pillar number so that the quadratic modes of the natural vibration of turbine moving blade is above in the operation range external resonance, therefore, can avoid with operation range in the quadratic modes of rotor blade more than resonance, can improve the reliability of turbine moving blade.
Preferably the concrete number with pillar is set at 6～12.The setting of this number helps the test result of shaking also to represent with Campbell's line chart by shown in Figure 10, parsing.According to this line chart characteristic, overtone order H should be 6～12.
Overtone order H is the excited frequency that causes according to the variation in pressure that the pillar number produces and the ratio of the rotating speed of turbine moving blade; For example; When pillar is 5; Confirm the relation of rotating speed and vibration frequency at the 5H line, the intersection point of the eigentone of 5H line and turbine moving blade (pattern) becomes point of resonance K1.
Therefore, in eigentone, in order to become the resonance state of alap rotating speed; Need be more than the 6H line, and, operation range left in order to make the intersection point with eigentone more than the quadratic modes; Need make overtone order below the 10H line, yet, about quadratic modes; According to the parsing that helps the test result of shaking, to compare with pattern or tertiary mode, the stress that the turbine moving blade 50 when resonance produces is little; Therefore, preferably will be used to avoid the overtone order of the resonance of tertiary mode to be chosen as below the 12H line.
Therefore, in eigentone, in order to become slow-revving as far as possible resonance state, need be more than the 6H line, and leave below the 12H line of operation range three eigentones.
And, in first invention and second invention, preferably along circumferentially disposing said pillar with unequal-interval.Through pillar spacer being set with unequal-interval, can prevent the increase of the excitation force of CF, avoid and turbine moving blade between the superfluous danger that increases of the resonance stress that causes of resonance.
And in first invention and second invention, any of preferred said pillar is configured in the positive downstream of the tongue of the coiling end portion that constitutes volute portion.
Like this, through being arranged on the positive downstream of tongue, stop the exhaust gas that flows out from tongue directly to flow to central side through pillar; Therefore; Elimination is flow through the flow mobile distortion of the set part that flows with the inflow that flows into after the tongue of the inflow that comes from the volute portion of turbine shroud, that is, and and through strengthening mobile along turbine shroud; Near the mobile distortion of elimination tongue, the efficient that can suppress turbine moving blade reduces.
The invention effect
According to first invention of the present invention; Utilize pillar along turbine shaft to the parts on the cartridge housing side that the is provided with bearing parts with the flowing path outlet side in the outside that forms turbine moving blade are linked; The running shaft of this bearing supporting turbine moving blade, this pillar forms to the section shape of seeing at turbine shaft: the upstream side bight and the bight, downstream side of air-flow form acute angle respectively, and upstream side and downstream side tilt along air-flow; Therefore; With respect to making volute portion, can reduce the both sides of area of contour in area of contour and downstream side of the upstream side of pillar, thus while the air-flow that rotates towards central side; Can reduce by pillar cause to the gas stream flow channel resistance, can reduce the wake flow (flow and distort) that produces at the pillar rear.Its result can improve the mobile distortion of flowing behind the pillar, can improve the efficient and the reliability of turbine moving blade.
According to above-mentioned second invention; Owing to set the pillar number; A pattern of the excitation force that produces so that be configured in the circumferential variation in pressure of the inflow gas that circumferential a plurality of pillars cause and the natural vibration of said turbine moving blade is in the slow-speed of revolution side resonance of operation range; Therefore, prevent that a mode resonance stress of turbine moving blade is superfluous, the stress in the time of can reducing to resonate.And, set the pillar number so that the quadratic modes of the natural vibration of turbine moving blade is above in the operation range external resonance, therefore, can avoid with operation range in the quadratic modes of rotor blade more than resonance, can improve the reliability of turbine moving blade.
Description of drawings
Fig. 1 is the stereogram of schematic configuration of the turbine shroud of first embodiment of the invention.
Fig. 2 is the sectional drawing of major component of the A-A line of Fig. 1.
Fig. 3 is the cross sectional illustration figure of leg portion.
Fig. 4 is the explanatory drawing of the processing of expression pillar, (A) configuration status of expression cutting tool, and (B) expression remains with the roughly tetragonal section shape of inscribed circle arc, and (C) expression does not keep the section shape of the general triangular of inscribed circle arc.
Fig. 5 is the explanatory drawing of second mode of execution, is the section shape figure different with Fig. 4 of pillar.
Fig. 6 is the explanatory drawing of the 3rd mode of execution, is the explanatory drawing of the resonance of turbine moving blade.
Fig. 7 is the explanatory drawing of the 3rd mode of execution.
Fig. 8 representes the 4th mode of execution, is the explanatory drawing of spacing of the unequal interval of expression pillar.
Fig. 9 representes the 5th mode of execution, is that expression is with the explanatory drawing of pillar to the configuration of tongue downstream side.
Figure 10 is the explanatory drawing of the relation between the resonance of the expression excitation force that causes of pillar and turbine moving blade.
Figure 11 is the explanatory drawing of expression existing technology.
Embodiment
Below, the mode of execution shown in the utilization figure is elaborated to the present invention.Yet, for the size of the structure member of putting down in writing in this mode of execution, material, shape, its configuration etc. relatively, short ofly carry out specific record especially, just mean that this scope of invention is not limited only to this.
(first mode of execution)
With reference to Fig. 1～Fig. 4 the turbine shroud of first mode of execution of the present invention is described.
Like Fig. 1, shown in Figure 2, the turbine shroud 1 of sheet metal system roughly is made up of volute portion 3, center core 9 and outer pipe portion 23, and in addition, volute portion 3 is made up of the first volute portion 5 and the second volute portion 7 of configuration relatively.And, form turbine shroud 1 through above-mentioned four parts of welding joint.
In forming the volute portion 3 of gyrate gas passageway, these two parts of the first volute portion 5 and the second volute portion 7 are docked, its docking part is carried out welding joint, thus the formation gas passageway.Each volute portion has the section shape that the gas passageway is roughly divided equally.
Rotating center section in volute portion 3; Be provided with center core 9; This center core 9 is roughly cylindric on the whole; And have cartridge housing body 15 that disposes bearing and the flowing path outlet portion 17 that forms the gas outlet side, the running shaft of this bearing supporting turbine moving blade 50 (with reference to Fig. 3) is provided with a plurality of pillars 21 between this turbine case body 15 and flowing path outlet portion 17.
In order to ensure stream 19; This stream 19 is to make in volute portion 3 gas that flows along the vortex direction to the smooth and easy mobile stream of central side; And, be provided with a plurality of these pillars 21 along circumferentially having the compartment of terrain in the outside of turbine moving blade 50 for bearing housing 15 is combined with flowing path outlet portion 17.
And; Pillar 21 is by having following intensity and stable on heating material constitutes; That is, can cartridge housing body 15 be linked with flowing path outlet portion 17, even and the slit between the inner peripheral surface of turbine moving blade 50 and center core 9 is kept necessarily.
In addition, through the complete cycle welding, the outer pipe portion 23 of tubulose is bonded on the front end of flowing path outlet portion 17.
As shown in Figure 2; In the first volute portion 5 and the second volute portion 7; (thickness of slab is for roughly 1～3mm) forming processing, separately end face is docked each other and forms gyrate gas passageway, and front end is overlapped to the metallic sheet material of thin plate; Form weld part a from the outside through one-sided welded corner joint, this weld part a is formed on the whole vortex direction of volute portion 3.
In addition, welding is not only one-sided welded corner joint, also can the front end of metallic sheet material be docked each other, and, engage through the butt welding of welding this part.And metallic sheet material is made up of the refractory steel of austenite and stainless steel etc. and gets final product.
And; Along the periphery of cartridge housing body 15, flowing path outlet portion 17 welding joint is carried out in the end of 9 sides of center core separately of the first volute portion 5, the second volute portion 7; Periphery in flowing path outlet portion 17 forms weld part b, at the periphery formation weld part c of cartridge housing body 15.
In addition, because cartridge housing body 15, flowing path outlet portion 17 and the pillar 21 that links them are integrative-structures, therefore, cartridge housing body 15, flowing path outlet portion 17 and pillar 21 are to form through the cutting cutting with integrative-structure.Likewise, export pipeline 23 also forms through cutting.
Below, the processing method of the pillar 21 of the turbine shroud 1 that is arranged on said structure and the section shape of pillar 21 are described.
Fig. 3 representes from turbine shaft to the situation of a plurality of pillars of seeing circumferential configuration in 21 edges and the section shape of this pillar 21.Process pillar 21 through following mode; That is, the center core 9 roughly cylindraceous (with reference to Fig. 2) with turbine shroud 15 and flowing path outlet portion 17 is carried out machining, for example; Utilize cutting; Reservation is as the part of this pillar 21, and excises the part between them, forms stream 19 at the position of excision.
Shown in Fig. 4 (A), in the cutting that forms pillar 21, make cutting tool 30 be connected to the upstream side 32 of the section shape of pillar 21; Form the plane of upstream side tilt angle theta 1; And,, form the plane of downstream side tilt angle theta 2 with respect to downstream side 34.As an example, upstream side tilt angle theta 1 is about 20 °, and downstream side tilt angle theta 2 is set at about 70 °.In addition, from easily carrying out the aspect of machining, upstream side 32 is processed into plane with downstream side 34.
If 20 ° of θ 1 less thaies, then the section shape of pillar will be too flat, if guarantee the section area that intensity is required; The area that then is formed on the stream 19 between the pillar 21 will be narrow; And,, pillar 21 is reduced with respect to the area of contour of flow direction if θ 1 surpasses 70 °; The loss of the air-flow that causes by pillar 21 can not be reduced, the generation of wake flow (flow and distort) can not be reduced.Therefore, preferably be arranged in 20 °～70 ° the acute angle scope.In addition, be not only upstream side tilt angle theta 1, and downstream side tilt angle theta 2 too.
Shown in Fig. 4 (B); When reservation inscribed circle arc 36 ground carry out cutting; Form integral body through inscribed circle arc 36, external circular arc 37, upstream side 32, downstream side 34 and be roughly tetragonal section shape; Shown in Fig. 4 (C), when not keeping inscribed circle arc 36 ground and carry out cutting, form integral body and be roughly leg-of-mutton section shape through external circular arc 37, upstream side 32, downstream side 34.Through this processing, roughly the upstream side bight of quadrilateral or leg-of-mutton section shape forms θ 1, and the bight, downstream side forms θ 2, upstream side 32 and downstream side 34 is formed the section shape that tilts along air-flow.
Thus, the upstream side of pillar 21 32 is made up of the plane respectively with downstream side 34, and they are roughly quadrilateral or triangle on the whole; Therefore, the binding parts for circular keep the part as pillar through machining; And; Through the cutting of machining, can easily excise the part between them, it is easy that the processing of pillar 21 and manufacturing become.
And; The angle in upstream side bight and bight, downstream side forms the acute angle of θ 1, θ 2 respectively; And upstream side 32 tilts along air-flow with downstream side 34, therefore, while with respect to the air-flow that makes 3 rotations of volute portion towards central side; Can make the both sides of area of contour of area of contour and downstream side 34 of upstream side 32 of pillar littler, can reduce the loss of the air-flow that causes by pillar 21 and the generation of wake flow (flow and distort) than existing rectangular section shape.
Therefore; Through guaranteeing to guarantee and the rigidity in the slit of turbine moving blade and the section area of intensity; And be set at above-mentioned section shape; Just can reduce to improve the efficient and the reliability of turbine moving blade because the pressure loss of the air-flow that pillar causes is improved the mobile distortion of pillar wake flow.
(second mode of execution)
Below, with reference to Fig. 7, the pillars 40 different with first mode of execution to section shape describe.Shown in Fig. 5 (A), this second mode of execution is the opposite mode of execution of angular dependence on plane of plane and downstream side tilt angle theta 2 that makes the upstream side tilt angle theta 1 of first mode of execution.That is, be set at upstream side tilt angle theta 1 and be about 70 °, downstream side tilt angle theta 2 is about 20 ° inclined side, utilizes cutting tool that face is separately processed.
And, shown in Fig. 5 (B), when carrying out cutting, form and be roughly tetragonal section shape on the whole through inscribed circle arc 43, external circular arc 44, upstream side 45, downstream side 46 on the external circular arc of reservation 42 ground.Shown in Fig. 4 (C), when not keeping external circular arc 42 ground and carry out cutting, form and be roughly leg-of-mutton section shape on the whole through inscribed circle arc 43, upstream side 45, downstream side 46.Through this processing, roughly the upstream side bight of quadrilateral or leg-of-mutton section shape forms θ 1, the bight, downstream side forms θ 2, and upstream side 45 forms along the section shape of air-flow inclination with downstream side 46.
About the pillar 40 that has carried out this processing; Identical ground with above-mentioned first mode of execution; The angle separately in upstream side bight and bight, downstream side is the acute angle of θ 1, θ 2, and upstream side 45 tilts along air-flow with downstream side 46, therefore; For making volute portion 3 while the air-flow that rotates towards central side; Area of contour and the area of contour of downstream side 46 of the upstream side 45 of pillar 40 can be reduced, thus, the loss of the air-flow that causes by pillar 40 and the generation of wake (flow and distort) can be reduced.In addition, since identical with respect to the area of contour of flow direction with first mode of execution, therefore, have the effect of the generation of windage loss identical with first mode of execution, that minimizing pillar 21 causes and minimizing wake flow (flow and distort).
(the 3rd mode of execution)
Below, with reference to Fig. 6, Fig. 7, Figure 10 the 3rd mode of execution is described.
About the establishing method of the number of above-mentioned pillar 21, in the 3rd mode of execution, set the number of pillar 21 with the mode of the synchronous vibration of avoiding turbine moving blade 50.
As shown in Figure 6, circumferentially pillar 21 is being set with equally spaced spacing P, the air-flow of gas becomes flowing towards the central side of turbine moving blade 50 from the eddy flow of volute portion 3.At this moment, can produce wake (flow distort) in the downstream side of pillar 21, therefore, in the downstream part of pillar 21 and the part between the pillar 21, the air-flow of the central side of entering turbine moving blade 50 can produce speed difference, promptly, pressure difference.Because this pressure difference circumferentially producing variation in pressure, produces the pressure wave F that dotted line is represented, produces excitation force.If this excitation force arrives turbine moving blade 50 sides, the eigentone of the vibration frequency of said excitation force and turbine moving blade 50 may produce resonance.Like this, below, the resonance of the vibration that the circumferential pressure ripple that is produced by the number according to pillar 21 causes and the eigentone of turbine moving blade 50 is called harmonic resonance.
Therefore, shown in figure 10, the vibration of turbine moving blade is resolved, estimate with Campbell's line chart.In this line chart, the longitudinal axis representes that vibration frequency, transverse axis represent that the rotating speed of turbine moving blade, straight line represent overtone order H.Overtone order H is the excitation force that causes according to the variation in pressure that the pillar number produces and the ratio of the rotating speed of turbine moving blade 50; For example; When the pillar number is five, the relation of representing by the 5H line represent the rotating speed of turbine moving blade 50 and the vibration frequency that produced at that time between relation.
Till Nmax, represent the service firing zone of turbine moving blade 50, and be set with an eigentone of turbine moving blade 50 and the line of three eigentones respectively.The intersection point of the line of the eigentone of 5H line and turbine moving blade 50 (a pattern eigentone, tertiary mode eigentone) is the point of resonance of this vibrational mode.
Usually, because the resonance of low order pattern produces big dynamic stress, therefore,, need point of resonance be moved to slow-speed of revolution side in order to avoid this low subresonance reliably.Therefore, in eigentone,, should select more than the 6H line in order to become the resonance state of alap rotating speed.
Because the eigentone of twice above high order need be left operation range as much as possible; Therefore; According to Campbell's line chart shown in Figure 10 of resolving, expression helps the test result of shaking, need leave operation range with the intersection point of eigentone more than twice pattern.Therefore, though overtone order need be below the 10H line, yet; About twice pattern; According to the parsing that helps the test result of shaking, to compare with pattern or tertiary mode, the stress that the turbine moving blade 50 when resonance produces is little; Therefore, preferably will avoid the overtone order of the resonance of tertiary mode to be chosen in below the 12H line.
Therefore, in eigentone,, more than the 6H line, and become below the 12H line that departs from operation range three eigentones in order to become the resonance state of alap rotating speed.
Therefore, preferred overtone order H is 6～12, and the number of pillar 21 should be at 6～12.Configuration example when for example, Fig. 9 representes that pillar 21 is 8.As shown in Figure 9,8 pillars 21 prevent the increase of the resonance stress of the turbine moving blade 50 that harmonic resonance causes with uniformly-spaced configuration.
And; The diameter of the inscribed circle arc 36 of pillar 21 is set in more than 1.15 of position of the external diameter of turbine moving blade 50; Guarantee the diffusion distance of the wake flow (flow and distort) of the rear flow side generation of pillar 21; And the pressure wave F that the circumferential variation in pressure that produces owing to pillar 21 causes does not get into rotor blade 50 sides, thereby further prevents the generation of harmonic resonance.
As stated; In the 3rd mode of execution; A pattern of the excitation force that produces owing to the circumferential variation in pressure that is configured in the inflow gas that circumferential a plurality of pillars 21 cause and the natural vibration of turbine moving blade 50 is in the slow-speed of revolution side resonance of operation range; Therefore, it is superfluous that a pattern resonating pressure that prevents turbine moving blade 50 becomes, the stress in the time of can reducing to resonate.
In addition and since with the tertiary mode of the natural vibration of turbine moving blade 50 in the operation range external resonance, therefore, can avoid the resonance in the tertiary mode of the turbine moving blade 50 in operation range, can improve the reliability of turbine moving blade.
(the 4th mode of execution)
Below, with reference to Fig. 8 the 4th mode of execution is described.
The 3rd mode of execution to be uniformly-spaced being provided with pillar 21, and the 4th mode of execution is provided with pillar 21 with the spacing of unequal interval.As shown in Figure 8, both can only make any spacing different with other spacings, also can make all spacings of P1～P8 all different.
Like this,, can prevent the increase of the excitation force of CF through the interval of pillar 21 is set with unequal-interval, avoid and turbine moving blade 50 between the superfluous danger that increases of the resonance stress that causes of resonance.Through making all spacings is unequal interval, can be reliably and suppress the generation of the excitation force of CF simply.
(the 5th mode of execution)
Below, with reference to Fig. 9 the 5th mode of execution is described.
At the 5th mode of execution,, be configured in the positive downstream of the tongue 52 of the coiling end portion that constitutes volute portion 3 like the pillar 21 of Fig. 9.
Like this; For example; To the number of pillar 21 is that 8 situation describes, if as illustrated in fig. 7 with uniformly-spaced from the position anticlockwise of the center line C of turbine moving blade 50 pillar 21A～21H is set, then pillar 21H is positioned at than tongue 52 and more leans on the sense of rotation upstream side; Therefore, flow into from gas such as the gas stream G1 ground that tongue 52 is discharged.Like this, conflict with G1 owing to flow through the stream S that circles round that comes from volute portion 3, therefore, the mobile set part with the stream S that circles round of the inflow after just flowing into tongue 52 can produce the distortion of flowing.
Yet,, be positioned at the positive downstream of tongue 52 through making pillar 21H like this mode of execution five ground; Like air-flow G2 ground, stop from tongue 52 effluent airs directly to the flowing of central side, especially through pillar 21H; Downstream side through along pillar 21H flows; And flow along flow through the eddy flow S that comes from volute portion 3, just having flowed into the mobile distortion that inflow after the tongue 52 flows with the concentrated part of the stream S that circles round and be eliminated, the efficient that can suppress turbine moving blade 50 reduces.
Industrial applicibility
According to the present invention relates to a kind of pillar; The parts of parts and exhaust flow path outlet side on turbine case side of bearing that its gas flow path ground that crosses the outer circumferential side of turbine moving blade will dispose the running shaft of supporting turbine moving blade link also integrated; It not only can reduce flow path resistance and improve to flow into characteristic, and can avoid the resonance of turbine moving blade, can improve the durability and the reliability of turbine moving blade; Therefore, be suitable for the turbine shroud structure.
Claims (8)
1. sheet metal system turbine shroud, this sheet metal turbine shroud forms volute portion with the scroll member relative bonding of sheet metal system, and this volute portion constitutes the exhaust gas stream of volute, it is characterized in that,
Outer circumferential side at turbine moving blade disposes a plurality of pillars along circumferentially having the compartment of terrain; This pillar links the running shaft of this bearing supporting turbine moving blade along turbine shaft to the parts to the parts on the cartridge housing side that is provided with bearing and the flowing path outlet side in the outside that forms turbine moving blade.
2. sheet metal system turbine shroud according to claim 1; It is characterized in that; Each said pillar at turbine shaft to the section shape of seeing is: the upstream side bight and the bight, downstream side of air-flow form acute angle respectively, and upstream side and downstream side tilt along air-flow.
3. sheet metal system turbine shroud according to claim 1 and 2 is characterized in that, the upstream side bight of the section shape of said pillar and the angle separately in bight, downstream side are 20 °～70 °.
4. sheet metal system turbine shroud according to claim 1 and 2; It is characterized in that; The section shape of said pillar is to have the roughly quadrilateral that inscribed circle arc, external circular arc, upstream side and downstream side constitute; Perhaps, any one of said inscribed circle arc or external circular arc do not have the general triangular of width.
5. sheet metal system turbine shroud according to claim 1 and 2; It is characterized in that; Set the number of pillar; So that a pattern of the natural vibration of excitation force that the circumferential variation in pressure of the inflow gas that causes owing to these a plurality of pillars produces and said turbine moving blade is in the slow-speed of revolution side resonance of operation range, and resonate with the rotating speed operation range outside more than the quadratic modes of the natural vibration of said turbine moving blade.
6. according to claim 1 or 2 or 5 described sheet metal system turbine shrouds, it is characterized in that the number of said pillar is set to 6～12.
7. according to claim 1 or 2 or 5 described sheet metal system turbine shrouds, it is characterized in that, along circumferentially said pillar being set with unequal-interval.
8. according to each described sheet metal system turbine shroud of claim 1～7, it is characterized in that any of said pillar is configured in the positive downstream of the tongue of the coiling end portion that constitutes volute portion.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2009-289414 | 2009-12-21 | ||
| JP2009289414A JP5357738B2 (en) | 2009-12-21 | 2009-12-21 | Turbine housing |
| PCT/JP2010/072584 WO2011078035A1 (en) | 2009-12-21 | 2010-12-15 | Turbine housing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102472115A true CN102472115A (en) | 2012-05-23 |
| CN102472115B CN102472115B (en) | 2015-06-03 |
Family
ID=44195565
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201080029321.4A Expired - Fee Related CN102472115B (en) | 2009-12-21 | 2010-12-15 | Turbine housing |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US9194292B2 (en) |
| EP (2) | EP3260670B1 (en) |
| JP (1) | JP5357738B2 (en) |
| KR (1) | KR101329507B1 (en) |
| CN (1) | CN102472115B (en) |
| WO (1) | WO2011078035A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109312659A (en) * | 2016-12-21 | 2019-02-05 | 三菱重工发动机和增压器株式会社 | The nozzle vane and turbine of turbocharger, turbocharger |
| CN110056400A (en) * | 2014-07-03 | 2019-07-26 | 三菱重工发动机和增压器株式会社 | Turbine case and its manufacturing method, turbine, the type core for casting turbine case |
| EP4411109A3 (en) * | 2023-02-01 | 2024-08-14 | Hamilton Sundstrand Corporation | Metal plated additively manufactured plastic housing |
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| JP5769407B2 (en) * | 2010-02-01 | 2015-08-26 | 三菱重工業株式会社 | Sheet metal turbine housing |
| DE102012209562B4 (en) * | 2012-06-06 | 2017-08-31 | Continental Automotive Gmbh | Turbine housing for an exhaust gas turbocharger |
| DE102012209560A1 (en) * | 2012-06-06 | 2013-12-12 | Continental Automotive Gmbh | Turbine housing for turbocharger, has contour component that is provided with sealing contour realized as cast portion or forging device welded to neighboring housing portions |
| JP2015140689A (en) * | 2014-01-27 | 2015-08-03 | 株式会社三五 | turbine housing |
| EP3112633B1 (en) * | 2014-02-28 | 2020-05-13 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Sheet metal turbine housing |
| JP6204398B2 (en) * | 2015-03-23 | 2017-09-27 | カルソニックカンセイ株式会社 | Turbine housing |
| WO2017078088A1 (en) * | 2015-11-06 | 2017-05-11 | カルソニックカンセイ株式会社 | Turbine housing |
| US10494955B2 (en) | 2017-01-30 | 2019-12-03 | Garrett Transportation I Inc. | Sheet metal turbine housing with containment dampers |
| US10544703B2 (en) | 2017-01-30 | 2020-01-28 | Garrett Transportation I Inc. | Sheet metal turbine housing with cast core |
| US10472988B2 (en) | 2017-01-30 | 2019-11-12 | Garrett Transportation I Inc. | Sheet metal turbine housing and related turbocharger systems |
| US10436069B2 (en) | 2017-01-30 | 2019-10-08 | Garrett Transportation I Inc. | Sheet metal turbine housing with biaxial volute configuration |
| US10690144B2 (en) | 2017-06-27 | 2020-06-23 | Garrett Transportation I Inc. | Compressor housings and fabrication methods |
| DE102018105827A1 (en) * | 2018-03-14 | 2019-09-19 | Man Energy Solutions Se | Formwork of a turbocharger and turbocharger |
| DE102018221161B4 (en) * | 2018-12-06 | 2021-08-26 | Vitesco Technologies GmbH | Exhaust gas turbine of an exhaust gas turbocharger and an exhaust gas turbocharger with a flow-related disruptive element in the turbine housing |
| US11732729B2 (en) | 2021-01-26 | 2023-08-22 | Garrett Transportation I Inc | Sheet metal turbine housing |
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- 2010-12-15 WO PCT/JP2010/072584 patent/WO2011078035A1/en active Application Filing
- 2010-12-15 KR KR1020117031317A patent/KR101329507B1/en active IP Right Grant
- 2010-12-15 US US13/384,913 patent/US9194292B2/en not_active Expired - Fee Related
- 2010-12-15 EP EP10839268.9A patent/EP2441924B1/en not_active Not-in-force
- 2010-12-15 CN CN201080029321.4A patent/CN102472115B/en not_active Expired - Fee Related
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| EP4411109A3 (en) * | 2023-02-01 | 2024-08-14 | Hamilton Sundstrand Corporation | Metal plated additively manufactured plastic housing |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2011078035A1 (en) | 2011-06-30 |
| JP5357738B2 (en) | 2013-12-04 |
| US9194292B2 (en) | 2015-11-24 |
| JP2011127575A (en) | 2011-06-30 |
| US20120275914A1 (en) | 2012-11-01 |
| EP2441924A1 (en) | 2012-04-18 |
| EP3260670B1 (en) | 2020-01-15 |
| KR101329507B1 (en) | 2013-11-13 |
| EP2441924B1 (en) | 2018-01-24 |
| KR20120015458A (en) | 2012-02-21 |
| EP2441924A4 (en) | 2014-07-09 |
| EP3260670A1 (en) | 2017-12-27 |
| CN102472115B (en) | 2015-06-03 |
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